This research applies a numerical study of topology optimization of laminate composite structures by using a Finite Element Method. In this methodology, the plies orientation is excluded from the optimization. The geometry-based optimization from frames of a MALE UAV fuselage structure is presented. The minimum strain energy with an optimization constraint of 20 percent of weight reduction is used in the objective function. Before the primary analysis, benchmark studies of topology optimization without considering orientations from previously published literature are performed. The convergence studies were taken to acquire the appropriate mesh size in the FEM technique, which utilized a four-noded shell element. The FE analysis and optimization results showed that the structural design of the newly frame composite fuselage MALE UAV meets the structural strength requirements specified in the airworthiness standard STANAG 4671.